The Excelsior was designed to comply with the US FAR 103 Ultralight Vehicles rules, including the category's maximum empty weight of 2540NaN0. The aircraft has a standard empty weight of 2500NaN0. It features a strut-braced high-wing, a single-seat, open cockpit, tricycle landing gear and a single engine in pusher configuration.
The aircraft fuselage is made from welded 4130 steel tubing, with the wings and tail built from riveted sheet aluminum, aluminum tubing and covered with doped aircraft fabric covering. Its straight leading edge, tapered trailing edge, 34.61NaN1 span wing is braced with a single lift strut per side. The pilot sits in an open cockpit, with a small windshield. The engine and tail configuration are unconventional. The specified Zenoah G25 200NaN0 engine is mounted on top of the high wing and drives the tail-mounted propeller through a flexible extension shaft, that is designed to eliminate vibrations. The tailplane and elevator are mounted on top of the rear fuselage, with the fin and rudder mounted below the tailplane, providing protection for the propeller from contacting the ground. The controls are conventional, except that roll control is provided by spoilers, rather than ailerons. The landing gear consists of suspended main gear, a nose wheel and a rudder-mounted rear skid.
The aircraft has enough gliding performance to be soared. The construction time from the plans is estimated at 400 hours. Plans were intermittently available between 1980 and about 2000, but from 2001 the design was not advertised as being available by the company any longer.[5]
